Apparatus and method of improving spacecraft attitude stability

A spacecraft and stability technology, applied in attitude control and other directions, can solve problems such as moment gyro vibration spacecraft

Active Publication Date: 2016-01-20
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a device and method for improving the attitude stability of the spacecraft in order to solve the vibration of the single-frame control moment gyroscope and how to improve the attitude stability of the spacecraft

Method used

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  • Apparatus and method of improving spacecraft attitude stability
  • Apparatus and method of improving spacecraft attitude stability

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Experimental program
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Embodiment 1

[0065] A six-degree-of-freedom decoupling vibration isolation method for a single-frame control moment gyroscope can be completed through the following steps:

[0066] A device for improving the attitude stability of a spacecraft, named as a vibration isolation element; the vibration isolation element includes an inner sleeve 1 and an outer sleeve 2; the inner sleeve 1 and the outer sleeve 2 are hollow cylinders with top ends; The diameter of the cross-section of the sleeve 1 is smaller than the diameter of the cross-section of the outer sleeve 2; the inner sleeve 1 is placed in the outer sleeve 2, and there is a gap between the inner sleeve 1 and the outer sleeve 2, and the metal spring 3 is placed in the gap, and the metal spring 3 is placed in the gap. The number of springs 3 is five, of which one metal spring 3 is located in the gap at the top, and the other four are evenly distributed in the gaps of the cylinder wall; the inner sleeve 1 of the vibration isolation element i...

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Abstract

The invention relates to an apparatus and method of improving spacecraft attitude stability, belonging to the spacecraft attitude dynamics and vibration inhibition field. The framework bearing of each SGCMG is provided with a vibration isolation element; each vibration isolation element includes a plurality of metal springs respectively in connection with the internal wall and the external wall of the vibration isolation element through spherical hinges. The internal wall of the vibration isolation element sleeves the framework bearing of an SGCMG so as to be in connection with the framework bearing of the SGCMG; the external wall of the vibration isolation element is directly in fixed connection with a satellite body. The vibration isolation elements can effectively solve the vibration problem of an SGCMG, and possess a decoupling characteristic so as to effectively and rapidly realize the parameter design of vibration isolation elements; in addition, the vibration isolation elements can greatly improve satellite attitude stability.

Description

technical field [0001] The invention relates to a device and a method for improving the attitude stability of a spacecraft, belonging to the fields of attitude dynamics and vibration suppression of the spacecraft. Background technique [0002] Single Frame Controlled Moment Gyro (SGCMG) does not consume fuel during work, does not cause pollution to the space environment, and can provide a larger torque output than a flywheel, enabling the spacecraft to perform rapid attitude maneuvers at large angles. Therefore, it has become a commonly used actuator for spacecraft attitude control. In recent years, with the diversification of space missions and the rapidity of mission requirements, the spacecraft is required to have the ability to respond quickly, that is, the design of the spacecraft can be completed within three to five months after receiving the mission requirements of the spacecraft and manufacturing. Therefore, the generalization and modular design of some components...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 张尧李谋盛超李文博王有懿
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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